US20080075583A1 - Sealing of variable guide vanes - Google Patents

Sealing of variable guide vanes Download PDF

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Publication number
US20080075583A1
US20080075583A1 US11/979,721 US97972107A US2008075583A1 US 20080075583 A1 US20080075583 A1 US 20080075583A1 US 97972107 A US97972107 A US 97972107A US 2008075583 A1 US2008075583 A1 US 2008075583A1
Authority
US
United States
Prior art keywords
guide vane
sealing sleeve
guide
vane stem
housing
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Abandoned
Application number
US11/979,721
Other languages
English (en)
Inventor
Joel Schlienger
Adrian Kopp
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Accelleron Industries AG
Original Assignee
ABB Turbo Systems AG
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by ABB Turbo Systems AG filed Critical ABB Turbo Systems AG
Assigned to ABB TURBO SYSTEMS AG reassignment ABB TURBO SYSTEMS AG ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: KOPP, ADRIAN, SCHLIENGER, JOEL
Publication of US20080075583A1 publication Critical patent/US20080075583A1/en
Abandoned legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
    • F01D17/165—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for radial flow, i.e. the vanes turning around axes which are essentially parallel to the rotor centre line
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/02—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
    • F02B37/00—Engines characterised by provision of pumps driven at least for part of the time by exhaust
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use
    • F02C6/04—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output
    • F02C6/10—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output supplying working fluid to a user, e.g. a chemical process, which returns working fluid to a turbine of the plant
    • F02C6/12—Turbochargers, i.e. plants for augmenting mechanical power output of internal-combustion piston engines by increase of charge pressure
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/40—Application in turbochargers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/55—Seals
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/30—Retaining components in desired mutual position

Definitions

  • the disclosure relates to the field of turbomachines. It refers to the guiding device of a turbomachine, for example of the turbine of an exhaust gas turbocharger, with rotatably mounted, variable guide vanes, and also to an exhaust gas turbocharger with a turbine with such a guiding device.
  • Exhaust gas turbines for example of turbochargers, are used in conjunction with an internal combustion engine.
  • the exhaust gas from the internal combustion engine in this case is used as a propulsive means for driving the turbine wheel.
  • the turbine wheel is connected by means of a shaft to the compressor wheel, by which the inlet air, which is for feeding to the internal combustion engine, is compressed.
  • variable turbine geometries can be used in exhaust gas turbines instead of fixed flow cascades (nozzle ring).
  • the angle of incidence of turbine guide vanes can be adapted to the respective operating point by means of an adjusting mechanism.
  • a VTG device as a rule comprises a plurality of guide vanes which are mounted in a bearing housing, and an adjusting mechanism for rotating the guide vanes.
  • VTG devices are described for example in EP 0 226 444 or DE 43 09 636.
  • the guide vanes of an exhaust gas turbine which during operation are very intensely heated, must be installed in the bearing bushes with adequate radial clearance so that in the hot operating state they do not seize in the bearing bushes. Due to the radial clearance between the bearing bushes s and the guide vane stem, a small amount of hot gases always escapes from the region around the guide vane into the environment. With increasing bearing clearance, this leakage flow through the bearing bush increases. This effect leads to a loss of turbine efficiency, and also to an increased noise development, as a rule in the form of a whistling which becomes more and more intense.
  • An adjusting device for a guiding device of a turbomachine is disclosed to the effect that despite the operation-related clearance between the moving parts of the guiding device, no leakage flow, or only a slight leakage flow, escapes through the bearings of the guide vanes.
  • this can be realized by a sealing sleeve (also referred to as a sealing diaphragm or sealing element) being arranged between the housing, in which the guide vanes are rotatably mounted, and the respective guide vanes.
  • a sealing sleeve also referred to as a sealing diaphragm or sealing element
  • the sealing sleeve in this case is optionally axially guided through the cylindrical outside or inside diameter of the guide bush which is used for support of the guide vane stem.
  • a radial residual gap which possibly remains between the sealing sleeve and the guide bush, is tolerated to a minimum clearance so that only a small residual mass flow escapes through the fit.
  • an additional axial compression spring can ensure that the sealing sleeve is continuously pressed onto the guide vane mating contour, and that the axial gap and also the leakage flow are prevented as a result.
  • FIG. 1 shows a section through a part of an exhaust gas turbocharger, on the turbine side, with a guiding device with variable guide vanes.
  • FIG. 2 shows a section through a part of the guiding device according to FIG. 1 , with an unsealed guide vane, and
  • FIG. 3 shows a section through the arrangement according to FIG. 2 , with a guide vane which is sealed according to the disclosure.
  • variable guide vanes can be used on all turbomachines with guiding devices, for example exhaust gas turbochargers, power turbines, gas turbines or compressors, with variable guide vanes.
  • FIG. 1 shows the turbine side of an exhaust gas turbocharger with a turbine wheel 10 which is arranged in a turbine housing.
  • the turbine wheel comprises a hub 11 and rotor blades 12 which are fastened upon it or manufactured integrally with the hub.
  • the turbine housing comprises a gas inlet housing 21 , a bearing housing 22 , and also a partition 23 in the back of the hub of the turbine wheel.
  • the partition serves for the thermal shielding of the bearing housing from the hot turbine wheel. It can alternatively also be formed by parts of the bearing housing or the gas inlet housing.
  • a guiding device is arranged in the flow passage which leads to the rotor blades.
  • the guiding device comprises variable guide vanes 31 for controlling the exhaust gas flow 70 .
  • the guide vanes are rotatably mounted by a guide vane stem 32 in the turbine housing.
  • the guide vanes 31 can be rotated via an adjusting lever 41 around the axis of the guide 35 vane stem 32 .
  • the adjusting lever is driven via an adjusting ring 42 in order to position the guide vanes 31 in a defined set angle.
  • the guide vane stem 32 is mounted in the turbine housing with a small clearance.
  • the turbine housing in the region of the bearing of the guide vane stem, advantageously comprises guide bushes 50 which have a high abrasion resistance and a good slidability.
  • the guide bushes are pressed into the turbine housing and fixed.
  • the guide vane stem has a bearing 33 which is mounted inside the guide bush 50 in a sliding manner.
  • the guide vane stem can have a further bearing, e.g, on the end opposite the guide vane.
  • the axial support of the guide vanes as a rule is carried out via one or two axial stops or via the end of the guide vane stem on the one side and via the guide vane profile on the other side.
  • the axial locking of the guide vane can be ensured by means of compression springs.
  • the guide vanes which during operation are very intensely heated, must be installed with adequate radial clearance in the bearing bushes so that in the hot operating state they do not seize in the bearing bushes. Both in the region of the bearings 33 and also radially outside the mating contour 34 of the guide vanes, small gaps, through which leakage flows can flow out, ensue as a result.
  • sealing air can be introduced into the cavities 61 in the back of the partition.
  • This compressed air which is significantly colder in comparison to the exhaust gases, can be externally supplied, or, as shown in FIG. 1 , branched off at the compressor outlet and guided via a sealing air passage 62 to the turbine side.
  • the sealing air is guided into the cavities 61 and distributed along the entire circumference of the turbine.
  • the sealing air can have an at least slightly higher pressure than the exhaust gas flow 70 .
  • the sealing sleeve 80 is advantageously manufactured, and can be cast, turned or milled, from a heat-resistant steel. Depending upon the axial length of the axial gap which is to be bridged by the sealing sleeve, the sealing sleeve can be formed axially longer and more tubular, or else shorter and more annular.
  • the sealing sleeve has a cylindrical collar, a radially projecting, at least partially encompassing collar with an axial stop.
  • the sealing sleeve 80 in the exemplary embodiment which is shown, is supported by the cylindrical outside diameter of the guide bush 50 .
  • a possible radial gap between the sealing sleeve 80 and the guide bush 50 is tolerated to a minimum clearance.
  • This radial clearance between parts which, during operation, do not move or hardly move in relation to each other, can be kept significantly smaller than the clearance between the bearing 33 of the guide vane stem and the guide bush. Therefore, only a small residual mass flow, if any at all, escapes through the fit.
  • the additional axial compression spring 90 ensures that the sealing sleeve is continuously pressed onto the guide vane mating contour 34 and that the axial gap and also the leakage flow are prevented as a result.
  • the sealing sleeve can also be directly slipped onto a part of the turbine housing, for example if the guide bush of the guide vane bearing is not arranged in an accessible manner, or is completely absent.
  • the sealing sleeve would be supported by a cylindrical outside diameter of a housing component.
  • the sealing sleeve can alternatively also be radially guided inside the guide bush or inside a cylindrical recess of the turbine housing.
  • the sealing sleeve according to the disclosure therefore, prevents discharging of air or gases through the bearing of the guide vanes in exhaust gas turbines with or without sealing air supply, or in any other turbomachine with rotatably mounted, variable guide vanes.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • General Chemical & Material Sciences (AREA)
  • Supercharger (AREA)
  • Control Of Turbines (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
US11/979,721 2006-08-28 2007-11-07 Sealing of variable guide vanes Abandoned US20080075583A1 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP06405370.5 2006-08-28
EP06405370A EP1895106A1 (de) 2006-08-28 2006-08-28 Abdichtung verstellbarer Leitschaufeln
PCT/EP2007/058888 WO2008025749A1 (de) 2006-08-28 2007-08-27 Abdichtung verstellbarer leitschaufeln

Related Parent Applications (1)

Application Number Title Priority Date Filing Date
PCT/EP2007/058888 Continuation WO2008025749A1 (de) 2006-08-28 2007-08-27 Abdichtung verstellbarer leitschaufeln

Publications (1)

Publication Number Publication Date
US20080075583A1 true US20080075583A1 (en) 2008-03-27

Family

ID=37812631

Family Applications (1)

Application Number Title Priority Date Filing Date
US11/979,721 Abandoned US20080075583A1 (en) 2006-08-28 2007-11-07 Sealing of variable guide vanes

Country Status (6)

Country Link
US (1) US20080075583A1 (de)
EP (2) EP1895106A1 (de)
JP (1) JP2010501786A (de)
KR (1) KR20090035606A (de)
CN (1) CN101512107A (de)
WO (1) WO2008025749A1 (de)

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2112332A1 (de) 2008-04-23 2009-10-28 ABB Turbo Systems AG Trägerring einer Leitvorrichtung mit Sperrluftkanal
US20130089411A1 (en) * 2010-05-27 2013-04-11 Borgwarner Inc. Control shaft seal
EP2730744A1 (de) * 2012-11-08 2014-05-14 ABB Turbo Systems AG Abgasturbolader
US20140341761A1 (en) * 2011-06-15 2014-11-20 Emmanuel Severin Turbocharger Variable-Nozzle Assembly With Vane Sealing Ring
US20150315964A1 (en) * 2012-12-28 2015-11-05 Borgwarner Inc. Asymmetric actuator pivot shaft bushing for vtg turbocharger
US20160186568A1 (en) * 2013-06-13 2016-06-30 Continental Automotive Gmbh Turbocharger With a Radial-Axial Turbine Wheel
US20160312651A1 (en) * 2013-12-11 2016-10-27 Continental Automotive Gmbh Turbocharger
DE102016114253A1 (de) * 2016-08-02 2018-02-08 Man Diesel & Turbo Se Axialturbine eines Turboladers und Turbolader
US10533441B2 (en) 2017-06-02 2020-01-14 Rolls-Royce Corporation Floating interstage seal assembly
CN114961884A (zh) * 2022-04-27 2022-08-30 萍乡德博科技股份有限公司 一种汽油机涡轮增压可变截面喷嘴环的叶片组件、喷嘴环
US20230235681A1 (en) * 2020-06-23 2023-07-27 Turbo Systems Switzerland Ltd. Modular nozzle ring for a turbine stage of a continuous flow machine

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EP2072765A1 (de) * 2007-12-21 2009-06-24 ABB Turbo Systems AG Vorrichtung zur Druckanpassung
DE102008063212A1 (de) * 2008-12-29 2010-07-01 Continental Automotive Gmbh Welleneinrichtung mit wenigstens einer Dichtungsvorrichtung
WO2010092945A1 (ja) * 2009-02-10 2010-08-19 川崎重工業株式会社 ガスエンジンシステムおよびその制御方法
DE102009009129B4 (de) * 2009-02-17 2022-11-03 BMTS Technology GmbH & Co. KG Turbolader mit variabler Turbinengeometrie
DE102009055865B4 (de) 2009-11-26 2021-06-24 Ihi Charging Systems International Gmbh Verstelleinrichtung für eine Aufladeeinrichtung
DE102011104065A1 (de) * 2011-06-11 2012-12-13 Daimler Ag Abgasturbolader für eine Verbrennungskraftmaschine eines Kraftwagens
DE102012012000B4 (de) * 2012-06-16 2022-12-01 Volkswagen Aktiengesellschaft Turbine für einen Abgasturbolader
CN103410603B (zh) * 2013-07-02 2015-08-26 中国兵器工业集团第七0研究所 一种涡轮增压器磁悬浮式密封结构
CN103352729B (zh) * 2013-08-01 2016-03-16 河北工程大学 控制可调向心涡轮喷嘴环叶端间隙自适应调节装置及方法
EP2868868A1 (de) * 2013-11-05 2015-05-06 Siemens Aktiengesellschaft Montagevorrichtung und Montageverfahren einer Leitschaufel
JP7052263B2 (ja) * 2017-09-11 2022-04-12 いすゞ自動車株式会社 可変ノズルターボチャージャ
DE202021004007U1 (de) * 2020-10-21 2022-05-02 3BE Berliner Beratungs- und Beteiligungs-Gesellschaft mbH Radialgasturbine

Citations (4)

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Publication number Priority date Publication date Assignee Title
US2950084A (en) * 1953-10-15 1960-08-23 Power Jets Res & Dev Ltd Mounting of swivelling guide vane elements in elastic fluid machines
US3582231A (en) * 1968-07-26 1971-06-01 Sulzer Ag Bearing mount for vane rings of turboengines
US3674377A (en) * 1969-06-19 1972-07-04 Mtu Muenchen Gmbh Guide blading for turbo machines with adjustable guide vanes
US4659295A (en) * 1984-04-20 1987-04-21 The Garrett Corporation Gas seal vanes of variable nozzle turbine

Family Cites Families (4)

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Publication number Priority date Publication date Assignee Title
DE10253693B4 (de) * 2002-11-18 2005-12-01 Borgwarner Turbo Systems Gmbh Abgasturbolader
EP1426563A1 (de) * 2002-12-03 2004-06-09 BorgWarner Inc. Turbolader mit keramischer oder metallischer Hitzeisolierung zwischen Turbinen- und Lagergehäuse
EP1585888B1 (de) * 2003-01-10 2018-09-26 Honeywell International Inc. Turbolader
DE202005008606U1 (de) * 2005-06-02 2005-08-04 Borgwarner Inc., Auburn Hills Verstellwellenanordnung eines Turboladers

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2950084A (en) * 1953-10-15 1960-08-23 Power Jets Res & Dev Ltd Mounting of swivelling guide vane elements in elastic fluid machines
US3582231A (en) * 1968-07-26 1971-06-01 Sulzer Ag Bearing mount for vane rings of turboengines
US3674377A (en) * 1969-06-19 1972-07-04 Mtu Muenchen Gmbh Guide blading for turbo machines with adjustable guide vanes
US4659295A (en) * 1984-04-20 1987-04-21 The Garrett Corporation Gas seal vanes of variable nozzle turbine

Cited By (21)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2009130262A1 (de) * 2008-04-23 2009-10-29 Abb Turbo Systems Ag Trägerring einer leitvorrichtung mit sperrluftkanal
CN102016237A (zh) * 2008-04-23 2011-04-13 Abb涡轮系统有限公司 带有密封空气通道的引导装置的支撑环
JP2012500922A (ja) * 2008-04-23 2012-01-12 アーベーベー ターボ システムズ アクチエンゲゼルシャフト 遮断空気通路を有するガイド装置の支持リング
KR101244956B1 (ko) * 2008-04-23 2013-03-18 에이비비 터보 시스템즈 아게 실링 에어 채널을 가진 안내 장치의 캐리어 링
EP2112332A1 (de) 2008-04-23 2009-10-28 ABB Turbo Systems AG Trägerring einer Leitvorrichtung mit Sperrluftkanal
US9488182B2 (en) * 2010-05-27 2016-11-08 Borgwarner Inc. Control shaft seal
US20130089411A1 (en) * 2010-05-27 2013-04-11 Borgwarner Inc. Control shaft seal
US20140341761A1 (en) * 2011-06-15 2014-11-20 Emmanuel Severin Turbocharger Variable-Nozzle Assembly With Vane Sealing Ring
US8915704B2 (en) * 2011-06-15 2014-12-23 Honeywell International Inc. Turbocharger variable-nozzle assembly with vane sealing ring
EP2730744A1 (de) * 2012-11-08 2014-05-14 ABB Turbo Systems AG Abgasturbolader
CN103807006A (zh) * 2012-11-08 2014-05-21 Abb涡轮系统有限公司 排气涡轮增压器
US20150315964A1 (en) * 2012-12-28 2015-11-05 Borgwarner Inc. Asymmetric actuator pivot shaft bushing for vtg turbocharger
US9945287B2 (en) * 2012-12-28 2018-04-17 Borgwarner Inc. Asymmetric actuator pivot shaft bushing for VTG turbocharger
US20160186568A1 (en) * 2013-06-13 2016-06-30 Continental Automotive Gmbh Turbocharger With a Radial-Axial Turbine Wheel
US10190415B2 (en) * 2013-06-13 2019-01-29 Continental Automotive Gmbh Turbocharger with a radial-axial turbine wheel
US20160312651A1 (en) * 2013-12-11 2016-10-27 Continental Automotive Gmbh Turbocharger
US10808569B2 (en) * 2013-12-11 2020-10-20 Continental Automotive Gmbh Turbocharger
DE102016114253A1 (de) * 2016-08-02 2018-02-08 Man Diesel & Turbo Se Axialturbine eines Turboladers und Turbolader
US10533441B2 (en) 2017-06-02 2020-01-14 Rolls-Royce Corporation Floating interstage seal assembly
US20230235681A1 (en) * 2020-06-23 2023-07-27 Turbo Systems Switzerland Ltd. Modular nozzle ring for a turbine stage of a continuous flow machine
CN114961884A (zh) * 2022-04-27 2022-08-30 萍乡德博科技股份有限公司 一种汽油机涡轮增压可变截面喷嘴环的叶片组件、喷嘴环

Also Published As

Publication number Publication date
KR20090035606A (ko) 2009-04-09
EP2057352A1 (de) 2009-05-13
JP2010501786A (ja) 2010-01-21
CN101512107A (zh) 2009-08-19
WO2008025749A1 (de) 2008-03-06
EP1895106A1 (de) 2008-03-05

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AS Assignment

Owner name: ABB TURBO SYSTEMS AG, SWITZERLAND

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:SCHLIENGER, JOEL;KOPP, ADRIAN;REEL/FRAME:020149/0688

Effective date: 20071106

STCB Information on status: application discontinuation

Free format text: ABANDONED -- FAILURE TO RESPOND TO AN OFFICE ACTION